发明名称 |
COOLED TURBINE BLADE WITH DOUBLE COMPOUND ANGLED HOLES AND SLOTS |
摘要 |
A turbine blade for a gas turbine engine. The turbine blade includes a base having a blade root, a platform, a cooling air inlet, and a base air passageway. The turbine blade also includes an airfoil section adjoined to the base and having an outer wall, an airfoil air passageway, a plurality of trailing edge slots in fluid communication with the airfoil air passageway and a plurality of directional film holes through the outer wall in fluid communication with the airfoil air passageway. The plurality of directional film holes includes a first portion configured to discharge the cooling air toward a tip end, and a second portion configured to discharge the cooling air toward the platform. |
申请公布号 |
WO2014200871(A1) |
申请公布日期 |
2014.12.18 |
申请号 |
WO2014US41436 |
申请日期 |
2014.06.06 |
申请人 |
SOLAR TURBINES INCORPORATED |
发明人 |
ZHANG, LUZENG;YIN, JUAN;MOON, HEE K. |
分类号 |
F01D5/18;F01D5/30;F01D25/12;F02C7/12;F04D29/58 |
主分类号 |
F01D5/18 |
代理机构 |
|
代理人 |
|
主权项 |
|
地址 |
|